EP1287234B1 - Device for controlling the cooling flows of gas turbines - Google Patents
Device for controlling the cooling flows of gas turbines Download PDFInfo
- Publication number
- EP1287234B1 EP1287234B1 EP01951843A EP01951843A EP1287234B1 EP 1287234 B1 EP1287234 B1 EP 1287234B1 EP 01951843 A EP01951843 A EP 01951843A EP 01951843 A EP01951843 A EP 01951843A EP 1287234 B1 EP1287234 B1 EP 1287234B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- aforementioned
- nozzles
- inner barrel
- guide tube
- casing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Definitions
- the present invention relates to a device for controlling the cooling flows of gas turbines.
- gas turbines comprise a compressor, to which air is fed from the external environment so as to bring it up to pressure.
- the air under pressure passes into a series of combustion chambers which terminate in a nozzle and into each of which an injector feeds fuel which is mixed with the air so as to form a combustible air mixture to be burned.
- the turbine converts the enthalpy of the gases combusted in the aforementioned combustion chamber into mechanical energy available for a user.
- the present invention refers, in particular, to the outlet zone of the gas turbine compressor.
- the air supplied from the compression stages since it has been produced with considerable expenditure in terms of the thermodynamic cycle, must be used as far as possible for combustion, instead of for cooling or confining functions which moreover are required in the most critical hot zones.
- the problem which is posed in this context is therefore that of correct metering of this air in the various zones, taking into account that the amount of air required is variable depending on the operating conditions, the age and the degree of wear or soiling-of the turbine engine, its components and the dimensional variations of the components during the transients.
- Figures 1 to 3 show, respectively: a cross-sectional view of a gas turbine according to the prior art as described e.g. in US-A-4 807 433, denoted overall by the reference number 20; an enlarged view of the outlet zone of the compressor 21 of the gas turbine 20; and the conventional solution for controlling the cooling flows of the gas turbine 20 which may envisage fixed bores 22 in the body 50 of the inner barrel 23.
- Figure 1 shows a gas turbine 20 provided with a compressor 21 with which an inner barrel 23 and a load-bearing bolster 24 are associated; Figure 1 also shows, among other things, the rotors 25 and 26 of the turbine 20.
- the solutions currently used for correct metering of the air flows intended for cooling and sealing consist in the specific definition of orifices on the supply tubes/ducts and determination of the degree of play between rotating members and labyrinths formed in complementary stator components.
- Orifices and labyrinths are therefore interdependent from a design point of view and precisely determined during finalisation of the prototype, so that extreme situations and deviations in design can be safely handled.
- This air passing through a first barrier of labyrinth seals, then escapes from the vent of the load-bearing bolster 24 of the compressor 21 and through the front interspace of the first turbine rotor, through the labyrinth formed with the angel wings on the shanks of the blades and the stationary seals mounted on the casing.
- This air is therefore that of providing a seal from the oil vapours in the bolster 24 and hot gases inside the turbine 20, cooling the turbine disk and removing the heat produced by means of ventilation friction inside the inner barrel 23.
- An object of the present invention is therefore to provide a device for controlling the cooling flows of gas turbines which is able to allow the possibility of varying the air flow entering into the inner barrel, without the need for replacement of the latter.
- the invention aims to avoid any kind of disassembly of the most important components of the turbine engine, while allowing variation in the air flow into the inner barrel.
- Another object of the invention is to provide a device for controlling the cooling flows of the gas turbines which allows adjustment which is customized and repeatable over time, by simply stopping the machine and performing simple operations involving the selection and replacement of suitable component parts.
- a further final object of the invention is to provide a device for controlling the cooling flows of gas turbines which is advantageous from a cost point of view.
- an object of the invention is to provide a device for controlling the cooling flows of gas turbines which is substantially safe and reliable.
- a device for controlling the cooling flows of gas turbines where the aforementioned gas turbine is provided with a compressor with which an inner barrel and a load-bearing bolster are associated, characterized in that it envisages the arrangement of a plurality of replaceable nozzles which have an internal bore with different diameters and which can be mounted in suitable holes formed in the substantially cylindrical body of the aforementioned inner barrel so as to allow a variation in the flow of air entering into the aforementioned inner barrel, by means of the selection and replacement of at least some of the aforementioned nozzles with other nozzles having an internal bore with suitable diameters.
- each of the aforementioned nozzles has a threaded section able to engage with a corresponding internally threaded section present in a hole formed in the aforementioned inner barrel.
- each replaceable nozzle has a cylindrical section with a diameter smaller than that of the threaded section and a pair of incisions for engagement with a magnetic-head spanner.
- the nozzles are inserted by means of a guide tube and a magnetic-head spanner, the guide tube being inserted inside a corresponding hole present in the casing of the aforementioned compressor.
- the guide tube has a threaded collar for allowing engagement thereof with a corresponding hole present in the casing of the compressor.
- the guide.tube is inserted into the hole of the compressor casing by sliding it until the aforementioned threaded collar thereof is screwed into the corresponding threading of the compressor casing with its end inside the machine making contact with the aforementioned inner barrel, so as to form a retaining and guiding channel inside which the nozzles to be screwed into the body of the inner barrel can be passed.
- the holes in the compressor casing are closed using bolts, or other similar closing devices, inserted in position after removal of the guide tubes.
- the present invention relates, moreover, to the fact that, in order to fix the nozzles in the operating position, it is further envisaged using a dimpling punch, which is used by employing the guide tube as a guide for the striking point.
- the device for controlling the cooling flows of gas turbines is denoted overall by the reference number 10.
- the device 10 comprises a plurality of replaceable nozzles 11 which can be mounted in suitable holes 14 formed in the body 50 of the inner barrel 23.
- the nozzle 11 has a threaded section 12 able to engage with a corresponding internally threaded section 13 present in the hole 14.
- the nozzle 11 also has a cylindrical section 16 with a diameter smaller than the diameter of the threaded section 12 and the diameter of the innermost smooth section 14, and a pair of incisions 15 for engagement with a magnetic-head spanner.
- the invention also envisages the use of a special tool formed by a guide tube 17 and by the magnetic-head spanner.
- the guide tube 17 also has a threaded collar 18 allowing engagement thereof with a corresponding hole 19 present in the casing 27 of the compressor 21.
- the hole 19 therefore has an internally threaded section 40.
- the machining operations which must be carried out on the gas turbine 20 consist in the boring and threading of the external casing 27. of the compressor 21 and the boring and threading of the inner barrel 23.
- this area is divided up into a suitable number of nozzles 11 with cross-sections of suitable diameter, to be screwed onto the cylindrical body 50 of the inner barrel 23 radially inside suitable threaded bores 14.
- the replaceable nozzles. 11 obviously have internal bores 51 of suitable diameter.
- the replaceable nozzles 11 are in fact provided in the form of sets or kits, with various diameters of the internal bore 51, the average value of which corresponds to the nominally optimum design diameter.
- the diameter which is most appropriate on the basis of the readings provided by the machine instrumentation is then chosen.
- the special tool for mounting the replaceable nozzles consists, as already mentioned, of a guide tube 17 and an insertable spanner which is provided with a special magnetic cross head.
- the guide tube 17 has two ends provided with a flat cut perpendicular to the axis and a threaded collar 18 at one end, with a threading similar to that of the holes 19 for access to the casing 27 of the compressor 21.
- the guide tube 17 is inserted into the hole 19 of the casing 27 by sliding it until its threaded collar 18 is screwed into the corresponding threading of the casing 27.
- This operation brings the end inside the machine into contact with the inner barrel 23 so as to form a retaining and guide channel inside which the nozzles 11 to be screwed into the body 50 of the inner barrel 23 can be passed.
- the nozzles 11 are removed and inserted.
- the replaceable nozzles 11 must be fixed by means of dimpling, using the tube of the special tool, i.e. the guide tube 17, as a guide for the striking point.
- the guide tube 17 is then unscrewed and the screw plugs 41 are inserted in place of them, inside the hole 19, by means of the internal thread 40.
- the spanner has a magnetized head so as to be able to work easily with any angle of inclination.
- the solution proposed has the aim of being able to vary the flow of air entering into the inner barrel 23, without the need for replacement of the latter or in any case without the disassembly of any important component of the turbine engine, but by means of simple access to the replaceable nozzles 11 using a special tool, i.e. the guide tube 17, via holes 19 which are normally closed.
- This feature allows adjustment which is customised and repeatable over time, by simply stopping the machines and performing replacement with the appropriate calibrated nozzles.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Separation By Low-Temperature Treatments (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
- The present invention relates to a device for controlling the cooling flows of gas turbines.
- As is known, gas turbines comprise a compressor, to which air is fed from the external environment so as to bring it up to pressure.
- The air under pressure passes into a series of combustion chambers which terminate in a nozzle and into each of which an injector feeds fuel which is mixed with the air so as to form a combustible air mixture to be burned.
- The turbine converts the enthalpy of the gases combusted in the aforementioned combustion chamber into mechanical energy available for a user.
- The present invention refers, in particular, to the outlet zone of the gas turbine compressor.
- By way of introduction of the technical problems solved by the present invention, it should be noted that the constant attempt to increase the efficiency of gas turbines is subject to the requirement for optimisation of all the flows inside the turbine engines.
- In particular, the air supplied from the compression stages, since it has been produced with considerable expenditure in terms of the thermodynamic cycle, must be used as far as possible for combustion, instead of for cooling or confining functions which moreover are required in the most critical hot zones.
- The problem which is posed in this context is therefore that of correct metering of this air in the various zones, taking into account that the amount of air required is variable depending on the operating conditions, the age and the degree of wear or soiling-of the turbine engine, its components and the dimensional variations of the components during the transients.
- In fact, in the event of an insufficient air flow, the consequences are, at best, a significant reduction in the life of the components with the possibility of blade failure and fires.
- It is pointed out here, incidentally, that these factors may have a negative effect resulting in an increase in costs for users.
- In order to understand more fully the technical problems involved in the present invention, reference should be made first of all to Figures 1 to 3, which show, respectively: a cross-sectional view of a gas turbine according to the prior art as described e.g. in US-A-4 807 433, denoted overall by the
reference number 20; an enlarged view of the outlet zone of thecompressor 21 of thegas turbine 20; and the conventional solution for controlling the cooling flows of thegas turbine 20 which may envisagefixed bores 22 in thebody 50 of theinner barrel 23. - In greater detail, Figure 1 shows a
gas turbine 20 provided with acompressor 21 with which aninner barrel 23 and a load-bearingbolster 24 are associated; Figure 1 also shows, among other things, therotors turbine 20. - Examining in greater detail Figure 2, it is possible to see the
casing 27 and theblades 28, forming part of thecompressor 21, theoutlet diffuser 29 of thecompressor 21, theventing outlet 33 of the load-bearingbolster 24 and theair seals inner barrel 23; Figure 2 also shows a portion of therotor 32. - The solutions currently used for correct metering of the air flows intended for cooling and sealing consist in the specific definition of orifices on the supply tubes/ducts and determination of the degree of play between rotating members and labyrinths formed in complementary stator components.
- Orifices and labyrinths (see Figure 3) are therefore interdependent from a design point of view and precisely determined during finalisation of the prototype, so that extreme situations and deviations in design can be safely handled.
- This means that these adjustments and tolerances are therefore defined by the manufacturer during assembly.
- However, the need for an increase in the efficiency of the machines on the part of customers has resulted in a reduction in the air flows to the absolute minimum necessary, with the application of seals which are increasingly efficient - often excessively so - with the serious risks mentioned above.
- In particular, there has been a tendency to reduce the amount of air which escapes from the
compressor 21 towards the innermost portions of the machine 20 (Figures 1-2), in particular in the zone located inside theinner barrel 22. - This air, passing through a first barrier of labyrinth seals, then escapes from the vent of the load-bearing
bolster 24 of thecompressor 21 and through the front interspace of the first turbine rotor, through the labyrinth formed with the angel wings on the shanks of the blades and the stationary seals mounted on the casing. - The function of this air is therefore that of providing a seal from the oil vapours in the
bolster 24 and hot gases inside theturbine 20, cooling the turbine disk and removing the heat produced by means of ventilation friction inside theinner barrel 23. - Experience has shown that often, the compromise adopted between the need for an increase in efficiency and reliability of the machine, since there is no possibility for adjustment, has resulted in a sudden reduction in reliability of the machine.
- An object of the present invention is therefore to provide a device for controlling the cooling flows of gas turbines which is able to allow the possibility of varying the air flow entering into the inner barrel, without the need for replacement of the latter.
- More particularly, the invention aims to avoid any kind of disassembly of the most important components of the turbine engine, while allowing variation in the air flow into the inner barrel.
- Another object of the invention is to provide a device for controlling the cooling flows of the gas turbines which allows adjustment which is customized and repeatable over time, by simply stopping the machine and performing simple operations involving the selection and replacement of suitable component parts.
- A further final object of the invention is to provide a device for controlling the cooling flows of gas turbines which is advantageous from a cost point of view.
- Last but not least, an object of the invention is to provide a device for controlling the cooling flows of gas turbines which is substantially safe and reliable.
- These and other objects are achieved by a device for controlling the cooling flows of gas turbines, where the aforementioned gas turbine is provided with a compressor with which an inner barrel and a load-bearing bolster are associated, characterized in that it envisages the arrangement of a plurality of replaceable nozzles which have an internal bore with different diameters and which can be mounted in suitable holes formed in the substantially cylindrical body of the aforementioned inner barrel so as to allow a variation in the flow of air entering into the aforementioned inner barrel, by means of the selection and replacement of at least some of the aforementioned nozzles with other nozzles having an internal bore with suitable diameters.
- According to a preferred embodiment of the present invention, each of the aforementioned nozzles has a threaded section able to engage with a corresponding internally threaded section present in a hole formed in the aforementioned inner barrel.
- According to a further preferred embodiment of the present invention, each replaceable nozzle has a cylindrical section with a diameter smaller than that of the threaded section and a pair of incisions for engagement with a magnetic-head spanner.
- According to another preferred embodiment of the present invention, the nozzles are inserted by means of a guide tube and a magnetic-head spanner, the guide tube being inserted inside a corresponding hole present in the casing of the aforementioned compressor.
- More particularly, the guide tube has a threaded collar for allowing engagement thereof with a corresponding hole present in the casing of the compressor.
- The guide.tube is inserted into the hole of the compressor casing by sliding it until the aforementioned threaded collar thereof is screwed into the corresponding threading of the compressor casing with its end inside the machine making contact with the aforementioned inner barrel, so as to form a retaining and guiding channel inside which the nozzles to be screwed into the body of the inner barrel can be passed.
- According to yet another preferred embodiment of the present invention, during operation of the aforementioned gas turbine, the holes in the compressor casing are closed using bolts, or other similar closing devices, inserted in position after removal of the guide tubes.
- The present invention relates, moreover, to the fact that, in order to fix the nozzles in the operating position, it is further envisaged using a dimpling punch, which is used by employing the guide tube as a guide for the striking point.
- Further characteristic features of the invention are defined in the claims accompanying the present patent application.
- The further objects and advantages of the present invention, as well as its structural and functional characteristics, will emerge clearly from an examination of the description which follows and its accompanying drawings, which are provided purely by way of a nonlimiting example and in which:
- Figure 1 shows a cross-sectional view of a gas turbine according to the prior art;
- Figure 2 shows a cross-sectional view of an enlargement of the outlet zone of the compressor of the gas turbine according to Figure 1;
- Figure 3 shows the conventional solution for controlling the cooling flows of gas turbines, which envisages fixed bores in the body of the inner barrel;
- Figure 4 shows a partially sectioned view of a nozzle forming part of the device for controlling the cooling flows of the gas turbines, according to the present invention;
- Figure 5 shows a top plan view of the nozzle according to Figure 4;
- Figure 6 shows a partially sectioned view of the device for controlling the cooling flows of the gas turbines, according to the present invention, during a first assembly stage; and
- Figure 7 shows a partially sectioned view of the device for controlling the cooling flows of gas turbines, according to the present invention, in the operationally assembled condition.
- With particular reference firstly to Figures 6-7, the device for controlling the cooling flows of gas turbines, according to the present invention, is denoted overall by the
reference number 10. - The
device 10 comprises a plurality ofreplaceable nozzles 11 which can be mounted insuitable holes 14 formed in thebody 50 of theinner barrel 23. - With reference to Figures 4-5, the
nozzle 11 has a threadedsection 12 able to engage with a corresponding internally threadedsection 13 present in thehole 14. - The
nozzle 11 also has acylindrical section 16 with a diameter smaller than the diameter of the threadedsection 12 and the diameter of the innermostsmooth section 14, and a pair ofincisions 15 for engagement with a magnetic-head spanner. - The invention also envisages the use of a special tool formed by a
guide tube 17 and by the magnetic-head spanner. - The use of a dimpling punch is also envisaged.
- The
guide tube 17 also has a threadedcollar 18 allowing engagement thereof with acorresponding hole 19 present in thecasing 27 of thecompressor 21. - The
hole 19 therefore has an internally threadedsection 40. - As regards that stated above, the machining operations which must be carried out on the
gas turbine 20 consist in the boring and threading of theexternal casing 27. of thecompressor 21 and the boring and threading of theinner barrel 23. - Once the useful area necessary for a nominally correct value of air to be admitted into the
inner barrel 23 has been defined, this area is divided up into a suitable number ofnozzles 11 with cross-sections of suitable diameter, to be screwed onto thecylindrical body 50 of theinner barrel 23 radially inside suitable threadedbores 14. - Opposite these
bores 14, a corresponding number of threaded radial bores are formed in thecasing 27 of thecompressor 21, having the function of providing access to thereplaceable nozzles 11 from the outside. - During operation of the
gas turbine 20, theseholes 19 are closed bybolts 41 and other similar closing devices. - The replaceable nozzles. 11 obviously have
internal bores 51 of suitable diameter. - The
replaceable nozzles 11 are in fact provided in the form of sets or kits, with various diameters of theinternal bore 51, the average value of which corresponds to the nominally optimum design diameter. - Once the
gas turbine 20 has been started using this initially attempted diameter, the diameter which is most appropriate on the basis of the readings provided by the machine instrumentation is then chosen. - The special tool for mounting the replaceable nozzles consists, as already mentioned, of a
guide tube 17 and an insertable spanner which is provided with a special magnetic cross head. - The
guide tube 17 has two ends provided with a flat cut perpendicular to the axis and a threadedcollar 18 at one end, with a threading similar to that of theholes 19 for access to thecasing 27 of thecompressor 21. - From an operational point of view, the
guide tube 17 is inserted into thehole 19 of thecasing 27 by sliding it until its threadedcollar 18 is screwed into the corresponding threading of thecasing 27. - This operation brings the end inside the machine into contact with the
inner barrel 23 so as to form a retaining and guide channel inside which thenozzles 11 to be screwed into thebody 50 of theinner barrel 23 can be passed. - Therefore, after insertion of the magnetic head spanner, the
nozzles 11 are removed and inserted. - Once the replacement operation has been completed, the
replaceable nozzles 11 must be fixed by means of dimpling, using the tube of the special tool, i.e. theguide tube 17, as a guide for the striking point. - After this operation has been completed, the
guide tube 17 is then unscrewed and the screw plugs 41 are inserted in place of them, inside thehole 19, by means of theinternal thread 40. - The spanner has a magnetized head so as to be able to work easily with any angle of inclination.
- The theoretical and experimental results have been so satisfactory as to demonstrate that the system may be used on gas turbines which are widely used.
- Therefore, the solution proposed has the aim of being able to vary the flow of air entering into the
inner barrel 23, without the need for replacement of the latter or in any case without the disassembly of any important component of the turbine engine, but by means of simple access to thereplaceable nozzles 11 using a special tool, i.e. theguide tube 17, viaholes 19 which are normally closed. - This is such as to allow adjustment which is customised and repeatable over time by simply stopping the
machines 20 and replacing the appropriate calibratednozzles 11. - From the description given the characteristic features of the device for controlling the cooling flows of gas turbines forming the subject of the present invention clearly emerge, as do the advantages thereof.
- The following final comments and observations are added here so as to define the aforementioned advantages with greater precision and clarity.
- As a result of the invention described it is possible to vary the flow of air entering into the
inner barrel 23 by simply gaining access to theremovable nozzles 11 using a special tool, viaholes 19, which are normally closed. - This feature allows adjustment which is customised and repeatable over time, by simply stopping the machines and performing replacement with the appropriate calibrated nozzles.
- It is obvious that numerous variations may be made to the device for controlling the cooling flows of gas turbines, according to the present invention, without thereby departing from the novel features of the inventive idea described.
- Finally it is obvious that, in the practical embodiment of the invention, the materials, forms and dimensions of the details illustrated may be of any kind, depending on requirements, and that they may be replaced with others which are equivalent from a technical point of view.
- The scope of the invention is defined by the accompanying claims.
Claims (9)
- Device (10) for controlling the cooling flows of gas turbines (20), where the aforementioned gas turbine (20) is provided with a compressor (21) with which an inner barrel (23) and a load-bearing bolster (24) are associated, characterized in that it envisages the arrangement of a plurality of replaceable nozzles (11) which have an internal bore (51) with different diameters and which can be mounted in suitable holes (14) formed in the substantially cylindrical body (50) of the aforementioned inner barrel (23) so as to allow a variation in the flow of air entering into the aforementioned inner barrel (23), by means of the selection and replacement of at least some of the aforementioned nozzles (11) with other nozzles (11) having an internal bore (51) with suitable diameters.
- Device (10) according to Claim 1, characterized in that each of the aforementioned nozzles (11) has a threaded section (12) able to engage with a corresponding internally threaded section (13) present in a corresponding hole (14) formed in the body (50) of the aforementioned inner barrel (23).
- Device (10) according to Claim 2, characterized in that each of the aforementioned replaceable nozzles (11) has a cylindrical section (16) with a diameter smaller than that of the aforementioned threaded section (12).
- Device (10) according to Claim 2 or 3, characterized in that each of the aforementioned replaceable nozzles (11) has a pair of incisions (15) for engagement with a magnetic head spanner.
- Device (10) according to Claim 1, characterized in that the aforementioned nozzles (11) are inserted by means of a guide tube (17) and a magnetic head spanner, the aforementioned guide tube (17) being inserted inside a corresponding hole (19) present in the casing (27) of the aforementioned compressor (21).
- Device (10) according to Claim 5, characterized in that aforementioned guide tube (17) has a threaded collar (18) allowing engagement thereof with a corresponding hole (19) present in the casing (27) of the aforementioned compressor (21).
- Device (10) according to Claim 5 or 6, characterized in that the aforementioned guide tube (17) is inserted into the hole (19) of the casing (27) by sliding it until its threaded collar (18) is screwed into the corresponding threading of the casing (27) with the end inside the machine making contact with the aforementioned inner barrel (23), so as to form a retaining and guide channel inside which the aforementioned nozzles (11) to be screwed into the body of the inner barrel (23) can be passed.
- Device (10) according to Claim 5 or 6, characterized in that, during operation of the aforementioned gas turbine (20), the aforementioned holes (19) are closed by means of bolts (41) or other similar closing devices which are inserted in position after the aforementioned guide tubes (17) have been removed.
- Device (10) according to the preceding claims, characterized in that, in order to fix the aforementioned nozzles (11) in the operating position, it is further envisaged using a dimpling punch, which is used by employing the guide tube (17) as a guide for the striking point.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ITMI000106 | 2000-05-15 | ||
IT2000MI001061A IT1317538B1 (en) | 2000-05-15 | 2000-05-15 | DEVICE FOR THE CONTROL OF REFRIGERATION FLOWS OF GAS TURBINES |
PCT/IB2001/001297 WO2001088354A2 (en) | 2000-05-15 | 2001-05-15 | Device for controlling the cooling flows of gas turbines |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1287234A2 EP1287234A2 (en) | 2003-03-05 |
EP1287234B1 true EP1287234B1 (en) | 2006-10-11 |
Family
ID=11445041
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01951843A Expired - Lifetime EP1287234B1 (en) | 2000-05-15 | 2001-05-15 | Device for controlling the cooling flows of gas turbines |
Country Status (10)
Country | Link |
---|---|
US (1) | US6767182B2 (en) |
EP (1) | EP1287234B1 (en) |
JP (1) | JP4718746B2 (en) |
AU (1) | AU2001272691A1 (en) |
CA (1) | CA2407954C (en) |
DE (1) | DE60123784T2 (en) |
IT (1) | IT1317538B1 (en) |
RU (1) | RU2278289C2 (en) |
TW (1) | TW555930B (en) |
WO (1) | WO2001088354A2 (en) |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6693719B1 (en) * | 1998-09-16 | 2004-02-17 | Texas Instruments Incorporated | Path to trapezoid decomposition of polygons for printing files in a page description language |
FR2871398B1 (en) * | 2004-06-15 | 2006-09-29 | Snecma Moteurs Sa | METHOD FOR MANUFACTURING A TURBINE STATOR CASTER |
US7836694B2 (en) * | 2005-05-06 | 2010-11-23 | Honeywell International Inc. | Air bearing turbo cooling air flow regulating device |
US20060248887A1 (en) * | 2005-05-06 | 2006-11-09 | Honeywell International Inc. | Air bearing turbo cooling air flow regulating device |
DE102005025086B4 (en) * | 2005-05-26 | 2014-07-10 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for fine balancing the rotor of a gas turbine engine |
ITMI20061086A1 (en) * | 2006-06-01 | 2007-12-02 | Nuovo Pignone Spa | DEVICE TO OPTIMIZE COOLING IN GAS TURBINES |
US20080036209A1 (en) * | 2006-08-10 | 2008-02-14 | United Technologies Corporation | Assembly including a spring-energized polymeric seal |
US8181555B2 (en) * | 2007-04-03 | 2012-05-22 | Climax Portable Machine Tools, Inc. | Machine for boring, turning, and face grooving |
US7914253B2 (en) * | 2007-05-01 | 2011-03-29 | General Electric Company | System for regulating a cooling fluid within a turbomachine |
FR2926481B1 (en) * | 2008-01-23 | 2011-09-23 | Snecma | COOLING CHANNEL CLEANING IN A WALL |
US8240974B2 (en) * | 2008-03-21 | 2012-08-14 | United Technologies Corporation | Cold air buffer supply tube |
US8083236B2 (en) * | 2009-09-22 | 2011-12-27 | Hamilton Sundstrand Corporation | Staggered seal assembly |
US8266888B2 (en) | 2010-06-24 | 2012-09-18 | Pratt & Whitney Canada Corp. | Cooler in nacelle with radial coolant |
FR2964584B1 (en) * | 2010-09-10 | 2013-08-16 | Snecma | DEVICE AND METHOD FOR FREQUING ANTI-WEAR PIECE IN A HOLE LOCATED IN A TURBOJET COMPONENT |
JPWO2016143103A1 (en) | 2015-03-11 | 2017-11-30 | 株式会社東芝 | Turbine |
US9988943B2 (en) | 2015-04-27 | 2018-06-05 | United Technologies Corporation | Fitting for mid-turbine frame of gas turbine engine |
US10774874B2 (en) | 2018-08-06 | 2020-09-15 | General Electric Company | Fluid bearing assembly |
WO2020149854A1 (en) * | 2019-01-18 | 2020-07-23 | Siemens Aktiengesellschaft | Pre-swirler with pre-swirler plug for gas turbine engine |
EP3976925A1 (en) * | 2019-07-25 | 2022-04-06 | Siemens Energy Global GmbH & Co. KG | Pre-swirler adjustability in gas turbine engine |
JP7242597B2 (en) | 2020-03-12 | 2023-03-20 | 東芝エネルギーシステムズ株式会社 | turbine rotor |
RU2767433C1 (en) * | 2021-04-09 | 2022-03-17 | Общество с Ограниченной Ответственностью "Научно-Производственное Предприятие "Авиагаз-Союз+" | Multi-flow vortex turbine |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE71024C (en) | S. STRAUSS JR. in Frankfurt a. M., Töpfengasse 4 | Stapler for sample sheets, letters, fabrics and the like | ||
DD71024A3 (en) * | 1968-06-28 | 1970-01-20 | ||
US3936217A (en) * | 1975-01-31 | 1976-02-03 | Westinghouse Electric Corporation | Inspection port for turbines |
US4008977A (en) * | 1975-09-19 | 1977-02-22 | United Technologies Corporation | Compressor bleed system |
JPS5364112A (en) * | 1976-11-19 | 1978-06-08 | Hitachi Ltd | Gas turbine compressor |
US4254618A (en) * | 1977-08-18 | 1981-03-10 | General Electric Company | Cooling air cooler for a gas turbofan engine |
US4246757A (en) * | 1979-03-27 | 1981-01-27 | General Electric Company | Combustor including a cyclone prechamber and combustion process for gas turbines fired with liquid fuel |
GB2065234B (en) | 1979-12-06 | 1983-06-02 | Rolls Royce | Turbine stator vane tension control |
US4302941A (en) * | 1980-04-02 | 1981-12-01 | United Technologies Corporation | Combuster liner construction for gas turbine engine |
US4807433A (en) * | 1983-05-05 | 1989-02-28 | General Electric Company | Turbine cooling air modulation |
EP0128850B1 (en) * | 1983-05-31 | 1988-12-07 | United Technologies Corporation | Thrust balancing and cooling system |
US4668162A (en) | 1985-09-16 | 1987-05-26 | Solar Turbines Incorporated | Changeable cooling control system for a turbine shroud and rotor |
JP2768789B2 (en) * | 1990-03-05 | 1998-06-25 | 株式会社東芝 | Gas turbine rotor |
US5961279A (en) * | 1996-05-31 | 1999-10-05 | Atlantic Richfield Company | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
AU7242998A (en) * | 1997-12-11 | 1999-06-28 | Watson Cogeneration Company | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
US6050079A (en) * | 1997-12-24 | 2000-04-18 | General Electric Company | Modulated turbine cooling system |
-
2000
- 2000-05-15 IT IT2000MI001061A patent/IT1317538B1/en active
-
2001
- 2001-05-15 JP JP2001584724A patent/JP4718746B2/en not_active Expired - Fee Related
- 2001-05-15 RU RU2002133462/06A patent/RU2278289C2/en not_active IP Right Cessation
- 2001-05-15 EP EP01951843A patent/EP1287234B1/en not_active Expired - Lifetime
- 2001-05-15 DE DE60123784T patent/DE60123784T2/en not_active Expired - Lifetime
- 2001-05-15 CA CA002407954A patent/CA2407954C/en not_active Expired - Fee Related
- 2001-05-15 US US10/257,539 patent/US6767182B2/en not_active Expired - Lifetime
- 2001-05-15 WO PCT/IB2001/001297 patent/WO2001088354A2/en active IP Right Grant
- 2001-05-15 AU AU2001272691A patent/AU2001272691A1/en not_active Abandoned
- 2001-09-19 TW TW090123013A patent/TW555930B/en active
Also Published As
Publication number | Publication date |
---|---|
CA2407954A1 (en) | 2001-11-22 |
DE60123784D1 (en) | 2006-11-23 |
WO2001088354A2 (en) | 2001-11-22 |
EP1287234A2 (en) | 2003-03-05 |
CA2407954C (en) | 2009-04-14 |
ITMI20001061A0 (en) | 2000-05-15 |
IT1317538B1 (en) | 2003-07-09 |
US20030147741A1 (en) | 2003-08-07 |
US6767182B2 (en) | 2004-07-27 |
DE60123784T2 (en) | 2007-08-16 |
AU2001272691A1 (en) | 2001-11-26 |
JP2003533631A (en) | 2003-11-11 |
RU2278289C2 (en) | 2006-06-20 |
JP4718746B2 (en) | 2011-07-06 |
ITMI20001061A1 (en) | 2001-11-15 |
TW555930B (en) | 2003-10-01 |
WO2001088354A3 (en) | 2002-04-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1287234B1 (en) | Device for controlling the cooling flows of gas turbines | |
US10669852B2 (en) | Gas turbine | |
EP1512843B1 (en) | Method of assembling a gas turbine engine and rotor assembly | |
KR102193940B1 (en) | Vane ring assembly, assembly method thereof and gas turbine including the same | |
US10914182B2 (en) | Gas turbine | |
US9291099B2 (en) | Structure for extracting compressed air from compressor of gas turbine engine and gas turbine engine with the structure | |
KR102028591B1 (en) | Turbine vane assembly and gas turbine including the same | |
JP5080864B2 (en) | Apparatus for optimizing cooling in a gas turbine and gas turbine having the apparatus | |
KR102027199B1 (en) | Variable guide vane actuating device and gas turbine including the same | |
KR20200037672A (en) | Turbine blade | |
KR100769768B1 (en) | Device for controlling the cooling flows of gas turbines | |
KR101958110B1 (en) | Turbine stator, turbine and gas turbine comprising the same | |
CN107420136B (en) | Gas turbine | |
KR20190076937A (en) | Gas turbine for improving performance at part-load and control method thereof | |
KR20180128661A (en) | Vane assembly and gas turbine including vane assembly | |
KR101984402B1 (en) | Compressor and gas turbine comprising the same | |
KR102212880B1 (en) | Gas turbine | |
KR102566947B1 (en) | Sealing assembly and turbo-machine comprising the same | |
US20230399960A1 (en) | Device for pressurizing turbomachine downstream enclosure, and corresponding turbomachine | |
KR101914879B1 (en) | Blade of turbine and turbine and gas turbine comprising the same | |
KR101984397B1 (en) | Rotor, turbine and gas turbine comprising the same | |
KR102153015B1 (en) | Rotor disk assembly and gas turbine including the same | |
JP2022003252A (en) | Apparatus for controlling turbine blade tip clearance and gas turbine including the same | |
KR20230126094A (en) | Coupling structure of casings and Gas turbine comprising the same | |
KR20190041213A (en) | Conjunction assembly and gas turbine comprising the same |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20021216 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO SI |
|
RBV | Designated contracting states (corrected) |
Designated state(s): CH DE FR GB LI NL |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE FR GB LI NL |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REF | Corresponds to: |
Ref document number: 60123784 Country of ref document: DE Date of ref document: 20061123 Kind code of ref document: P |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: NV Representative=s name: SERVOPATENT GMBH |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20070712 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PFA Owner name: NUOVO PIGNONE HOLDING S.P.A. Free format text: NUOVO PIGNONE HOLDING S.P.A.#2, VIA FELICE MATTEUCCI#50127 FLORENCE (IT) -TRANSFER TO- NUOVO PIGNONE HOLDING S.P.A.#2, VIA FELICE MATTEUCCI#50127 FLORENCE (IT) |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 16 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: NL Payment date: 20160526 Year of fee payment: 16 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 20160527 Year of fee payment: 16 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20160530 Year of fee payment: 16 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MM Effective date: 20170601 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170531 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170531 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20180131 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170601 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170531 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20180529 Year of fee payment: 18 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20180529 Year of fee payment: 18 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 60123784 Country of ref document: DE |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20190515 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190515 Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20191203 |